Calculation of unsteady transonic flows using the integral equation method

Nixon, David

doi:10.2514/6.1978-13

Cited by 5 publications

(5 citation statements)

References 6 publications

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“…There, Mis the freestream Mach number; k the reduced frequency, k = uc/2U, where c denotes the chord; and £7 the undisturbed flow speed. <$> (0) and $ (7) denote the mean steady and the first harmonic component of the perturbation velocity potential, and H the amplitude of oscillation of the mean wing surface. 7* is defined 1 by: 7* =2-(2-y)M 2 .…”

Section: Iem Formulationmentioning

confidence: 99%

“…The modified procedure is illustrated here for the M= 2 case. $} 7) is determined as in FTRAN2 in all points, Which leads approximately to 0(NR 2 j/h 2 ) operations, in which R]/h 2 <N. For determining $J 7) the following accelerated procedure is suggested: 1) Determine $J 7 > as in FTRAN2 in a number N c of specially selected points (collocation points), with N C <N, which leads approximately to 0 [NN C ] operations.…”

Section: E(xy)=mentioning

confidence: 99%

“…2) Determine $>J 7) in the other points by series, expansions, polynomials, or interpolation. The N s coefficients of these series, expansions, etc., with N" 5 «7Vare easily determined by collocation in the collocation points.…”

Section: E(xy)=mentioning

confidence: 99%

“…At present the following set E is evaluated at NLR: (7) and 0<r<R n where R 0 =Q, R M = OQ, r and <p being polar coordinates. The modified procedure is illustrated here for the M= 2 case.…”

Section: E(xy)=mentioning

confidence: 99%

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Calculation of unsteady transonic flows with shocks by field panel methods

Hounjet

1982

AIAA Journal

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Fig. 2 Design chart to determine K B KB(W) f°r no afterbody. for negative afterbody from Fig. 3 K B(Hr} for negative afterbody as a function of afterbody length. (If you relabel the abscissa as R = P+2 9 this figure is applicable for all P and D with 0 " = 1, £/C r = -0.2, andB-+.Variation of K B(W) with respect to afterbody length is illustrated in Fig. 3 for the full range of B values. Note that for a fixed B the dependence of K B( W) on R is linear if R is less than or equal to unity. ConclusionClosed-form formulas have been presented for the interference factors K B(]V) for a body in the presence of a wing at supersonic speeds when a finite afterbody is introduced. In addition, formulas for K B(W) 's have been obtained for situations when the base of the body is forward of the trailing edge of the exposed root chord (negative afterbody). These formulas are valid subject to the restrictions inherent in the formulation of Ref. 2. RemarksSimilar to K B( W} , the body longitudinal center-of-pressure location can be determined in closed form. This work is currently in progress and will be reported later.

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Section: Iem Formulationmentioning

confidence: 99%

Section: E(xy)=mentioning

confidence: 99%

Section: E(xy)=mentioning

confidence: 99%

“…At present the following set E is evaluated at NLR: (7) and 0<r<R n where R 0 =Q, R M = OQ, r and <p being polar coordinates. The modified procedure is illustrated here for the M= 2 case.…”

Section: E(xy)=mentioning

confidence: 99%

See 2 more Smart Citations

Calculation of unsteady transonic flows with shocks by field panel methods

Hounjet

1982

AIAA Journal

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“…A detailed description of the integral equation method is given in Ref. 4. The rationale and detailed description of the transonic perturbation method are given by Nixon.…”

mentioning

confidence: 99%